This thesis focuses on the continued extension, validation, and application of combined thermal-structural reduced order models for nonlinear geometric problems. The first part of the thesis focuses on the determination of the temperature distribution and structural response induced by an oscillating flux on the top surface of a flat panel. This flux is introduced here as a simplified representation of the thermal effects of an oscillating shock on a panel of a supersonic/hypersonic vehicle.
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- Partial requirement for: M.S., Arizona State University, 2011Note typethesis
- Includes bibliographical references (p. 67-69)Note typebibliography
- Field of study: Aerospace engineering